JPH07500397A - Utility conduit enclosure for turbine engines - Google Patents

Abstract

(57) [Summary] This bulletin contains application data before electronic filing, so abstract data is not recorded.

Description

[Detailed description of the invention] Utility conduit enclosure for turbine engines field of invention The present invention relates to turbine engines, and more particularly to turbine engines for use in turbine engines. Relating to a utility distribution device.

Background of the invention In a turbine engine, various auxiliary equipment (utilities) are connected to the turbine engine. required for engine operation and management. For example, around the engine A network of conduits installed and branched axially and circumferentially is typically attached. It provides the distribution system necessary to transmit the functions of the band equipment. That is, These conduits carry electricity, fuel, compressed air, and oil between the engine and the main frame. and transmitting hydraulic fluid. In addition, for example, an aircraft generator is installed on the main frame. has been done.

In order to control the engine with even higher precision, we need to improve the precision of engine control. Installing additional utility conduits to the engine as required for the purpose is required. And most of these utility conduits need to carry electricity. established for.

According to the prior art, multiple hardwired electrical conduits are connected to the engine fan cage. An annular volume section (hereinafter referred to as fan/fan) provided between the base and the engine core. (referred to as the interface section). Carried by each electrical conduit The numerous electrical leads extending from the electrical conduits are On the way to the designated terminal, there is so-called "octopus" wiring around the engine. It is distributed in all directions in a distribution that looks like this.

These electrical conduits and electrical leads run axially and around various engine surfaces. It is made to spread in the circumferential direction of the wire, and is semi-permanently fixed to the surface of the wire engine. has been established. The engine surface includes the fan case and the engine core. Ru. These electrical conduits and electrical leads typically connect electrical conduits, e.g. An electrical conductor carrying electrical leads designated to perform various sensing or control functions. In the process of establishing the necessary electrical connections to assign the pipes, They are intertwined or superimposed on each other.

Note that electrical leads designated to perform the sensing or control functions described above must be The sensors or controllers are widely distributed around the outer periphery of the engine core and The designated electrical leads are directed to the other sensor or controller.

Electrical leads and conduits attached to the engine may be disconnected intermittently due to structural interference. or cause premature failure due to continuous wear or fraying. exposed to high degrees of heat, vibration and shock loads. In front of the underside of the engine installed in the aircraft. Electrical leads and wires that extend beyond the fan/fine interface section. Air conductors are susceptible to wear or fraying (the wear or fraying occurs when the engine Inadvertently during maintenance and repair or during scheduled engine removal/replacement. resulting in higher costs and reduced repair time and aircraft downtime. Stopping time becomes longer.

In addition to the actual aircraft down time, a great deal of time and effort is spent on electrical conduits or Lead wires, especially those that are secured by more than 200 clamps or clips Typically equipped with an extensive engine electrical network containing over 200 electrical leads. Electrical conduits or electric lines in engines with state-of-the-art electronic management systems Commonly needed to find hard-to-find defects or failures in air leads . Also, the same (considerable amount of time and effort) is required to identify the defective product after the failure has actually been discovered. Removing each of the many intertwined electrical leads in hardwired electrical conduits required for accurate replacement.

When finding, removing, and replacing damaged electrical conduits or electrical leads, Another problem with the prior art is that the thrust lever doors are quite heavy (each door has approximately 4 It weighs 53.6 kg (approximately 1000 bonds) and is commonly used. is an obstacle. i.e. these heavy thrust lever saddle doors The engine control section is designed to allow access to the outer periphery of the engine for adequate repair and maintenance. The aircraft must be pulled up away from the ). A further problem with the prior art is that many utility The tube passes through the engine's fan/core interface and thus Due to the complexity of dividing the fan into more easily transportable components, It takes a lot of time and effort to attach or remove the case from the engine. It is.

In view of the problems with the conventional technology mentioned above, at least one major airline is currently using According to one implementation, defective electrical conduits in aircraft engines are Since there are no methods to detect, repair or replace the fan/fine interface. electrical conduits that have been inspected and are operationally defective while installed in the Remove the engine itself, replace it with a new engine, and put the aircraft into operation immediately. We are trying to get back to where we can be. This method keeps a spare engine in stock (Obviously the cost will be higher because it is necessary, but Considering the long periods during which aircraft are grounded and the disruption of operations, this method It can be said that the cost is clearly a reasonable cost.

It is an object of the present invention to A number of electrical conduits are organized, protected and sectioned to prevent defective electrical conduits. The purpose is to facilitate quick removal and replacement of lead wires.

Summary of the invention That is, in other words, an object of the present invention is to improve the core and fan case of a turbine engine. Multiple utilities straddle the annular volume section provided between the Protective modular enclosure for easy removal and replacement of pipes The utility conduit is a modular enclosure removably coupled to.

Another object of the invention is to provide a means for zoning outgoing utility flows. It's there.

That is, according to the present invention, the engine core extending in the axial direction of the turbine engine and An annular volume section provided between the fan case and the fan case that extends outward in the radial direction. Modular Enclosure for Releasably Mounted Utility Conduits Straddling A closure is provided.

This enclosure is then integrated into the engine's utility distribution system. Quickly remove and replace defective utility conduits in the field by This makes it easier to operate the aircraft, thereby minimizing aircraft downtime.

Enclosures with one or more utility conduits suspected of being defective Once the engine has been removed from the This can proceed independently of schedule demands.

In particular, the conduit enclosure according to the invention terminates proximate both ends of the enclosure. Enclose multiple utility conduits that are The terminal ends of these conduits are An enclosure is installed at the end of multiple fan cases and engine cores where these conduits meet. provided in close proximity to both ends of the enclosure or in direct engagement with each end face of the enclosure. releasably attached through the interface. inside the enclosure A plurality of cover panels releasably attached to a plurality of side surfaces between and at each end of the The aircraft is housed in an enclosure for the purpose of inspecting and repairing stationary aircraft. access to incoming utility conduits, thereby allowing access to incoming utility conduits. provided to the tee conduits and interfaces housed in the enclosure. The necessary connections and reconnections can be made between specific delivery conduits in the engine area. Wear.

Additionally, multiple brackets connect the enclosure to the fan case and engine core. releasably fixed to the engine with rollers. Furthermore, the enclosure is placed close to the engine core. A plurality of laterally extending tabs on the plunger are connected to the closed thrust lever. - captured by the enclosure door, which provides an additional enclosure retention device. It is. radially outward from the enclosure in the face of the downstream edge of the fan case The annular fire protection rule that extends at the same time acts on the closed thrust lever saddle door and Provides a firewall between the fan case environment and the engine core environment.

Brief description of the drawing FIG. 1a is a side view of a gas turbine engine embodying the invention.

Figure 1b shows a gas turbine illustrating a typical prior art utility conduit distribution. FIG. 2 is a side view of the engine.

FIG. 2 is an isometric view of a gas turbine engine embodying the invention.

FIG. 3 is a diagram showing the conduit enclosure removed from the gas turbine engine of FIG. It is.

Detailed description of examples Figure Ia shows a conduit enclosure 5o according to the invention. This enclosure 5 o is between the engine core 2o and fan case 3o of the gas turbine engine 10 A plurality of utility guides straddling the annular volume part 4o provided in An enclosure for containing and protecting the tube 42, which allows the Prior art utility conduits 42, i.e. exposed and interconnected. Circuits of hard-wired conduits that are highly tangled and poorly organized The net is improved. This divides the total wiring/%-ness into three areas: Fan case 30, engine core 20, and an annular volume provided between them The conduit of the annular volume section 40, which is the third section, is protected by a protective This is achieved by housing it within the enclosure 50.

Next, with particular reference to FIGS. 2 and 3, the enclosure 50 has its entire serpentine It has a trapezoidal cross section over its length. In addition, the enclosure 50 is a fan case 3. a first end 52 disposed proximate to engine core 20; and a second end 62. and installed through this enclosure 50. A plurality of bridging utility conduits 42 are connected to a first one of the enclosure 50. A plurality of first terminals 44 provided at the end 52 and a plurality of first terminals 44 provided at the end 52 and a plurality of second terminals 46 provided at the second end 62 on the opposite side; Each is connected.

The first terminal 44 of the bridging conduit 42 is installed on the corresponding fan case side. The first term of the mating set provided in the utility conduit 32 The terminal 34 is releasably secured to the terminal 34. These connections are made through the first surface 54. Through one or more holes 56 provided in the It is done using means.

In a similar manner, the second terminal 46 on the opposite side of the bridging conduit 42 is Provided in the utility conduit 22 provided on the corresponding engine core side is releasably secured to the second terminal 24 in the The connection between the engine core and the engine core is completed. That is, the first The second end 6 of the enclosure 50 by the same method of connection as was made at the end 52. The connection of the second terminal 24 on the second side is made through the second side 64 of the enclosure 50. This is done through one or more holes 66 provided in the hole. enclosure 50 Holes 56 and 66 provided in the first surface 54 and second surface 64 of the Can accommodate single or multiple conduits depending on the utility conduit through which it passes. Can be done. Making the connections described above is well known to those skilled in the art (as is well known to those skilled in the art) For this purpose, via the first side 54 and/or the second side 64 of the enclosure 50. A variety of bulkhead attachments may be provided using shaped connectors.

The first end 52 and second end 62 of the enclosure 50 are connected to the fan case 30 and They are each releasably fixed to the engine core 20. Regarding the engine shaft center line and a plurality of A bracket 57 extending radially inward is attached to one or more of the fan case 30 sides. The first end connection point 58 is connected to the first end connection point 58 by using a suitable fixing means known in the art, such as a bolt 59. Releasably fixed.

In a similar manner, at or near the second end 62 of the enclosure 50 A plurality of other brackets 57 are attached to one or more of the ennon cores 20. It is releasably secured to the second end connection point 68 . According to the present invention, multiple targets terminals 24, 34, 44° 46 and connection points 58, 68 for a relatively short time (10~ 20 seconds), which allows the enclosure 50 to be removed and other Enables quick replacement of enclosures and therefore facilitates quick field removal This can minimize aircraft downtime. The bracket 57 is It has a flanged structure, and the engine core 20 or fan case 30 side Their respective mountings are shaped and shaped to match and correspond to the connection points 58.68. It is.

A fluid and/or electrical utility flow is directed through the enclosure 50. Ru. That is, the bridging utility conduit 42 runs within the enclosure 50. to fluidically connect the first end 52 and second end 62 of the enclosure 50 to each other. and/or an electrical connection between the engine core 20 and the fan case 30. flowing electricity, fuel, compressed air, oil and/or hydraulic fluids. What is fluid and electricity? Although it flows separately in a dedicated conduit 42, the inflow into a predetermined conduit is controlled by an enclosure. At the interface 70 housed in the engine compartment It can be redirected to a fixed delivery conduit.

In addition to the end connectors 44, 46, the interface 7 inside the enclosure 50 0 at the middle and/or at both ends 52.62 of the enclosure 50. The enclosure cover pad provided on the outer surface 51 of the enclosure 50 at This becomes possible by removing the flannel 53. These cover panels 53 It is fixed to the enclosure 50 by connection means using a plurality of bolts 55. .

A plurality of bridging utility conduits 42 housed in the enclosure 50 are , are branched through the interface 70, thereby connecting the fan case 30 and the engine. Optimum harness design for Jincore 20 becomes easy.

That is, through the interface 70, the layout of the utility conduit is , for specific fluid/electrical utility flows required for specific engine configurations. Therefore, it can be performed independently to the maximum extent possible. In particular, the utility flow is Interface 70 allows specific engine core or fan case area portion 1 00 (see FIG. 1), all the utilities required for this particular area portion 100 one or more dedicated delivery utility conduits containing utility leads; Directed through. A plurality of specific area portions 1.00 are connected to the fan case 30. Although it is located in both Jin Core 20, for clarity of the drawing Only three zone portions 100 are shown in FIG. utility lead wire , more pertinently according to the scheduled engine core area section 100. It is included in a dedicated conduit 74 depending on the type of utility. It is possible to eliminate the tangles and overlaps of utility lead wires. Wear.

For example, electrical lines that lead a given control or sensing function from a single conduit (these Electrical lines (which typically span a large area around the engine core) are - face 70 in charge of its designated engine area portion 100 Directed to a particular conduit 74.

Therefore, in particular for the organized distribution of conduits to the section 100 of the engine core. Therefore, it is possible to prevent the untidy distribution of conduits according to the prior art as shown in Figure 1b. can be done. Referring again to Figure 3, using well-known connection means, The ability to interconnect conduits at branch interface 70 allows for specific Only the conduits 42 necessary for the engine structure can be provided as desired. this minute Access to the branch interface 70 is provided by the enclosure 50 on the engine 10. when the cover panel 53 closest to the branch interface 70 is This becomes possible by removing. Optionally, enclosure 5o is engine 1 Off-the-engine bench test after removal from 0 for ine bench testing) to branch interface 7o. It can easily be approached.

The above explanation focuses on the utility flow to engine core 2o. However, the device according to the invention also The fan is connected to the engine core 2o through a similar dedicated conduit (not shown) This can also be applied to the utility flow to case 3o. Therefore, Both sides of the interface 70 between the engine core 2o and the fan case 3o or The conduits 42 extending from either side of the are segmented independently at the engine structure.

A firewall 90 is also provided on the outer surface 51 of the enclosure 5o. child The fire wall 9o is located on the downstream edge surface of the fan case 30, and extends radially outwardly from a first end 52 of.

A fire wall seal line 92 having a spherical sole cross section is attached to the outer periphery of the fire wall 9o. is provided in contact with the corresponding inner surface of the surrounding engine case panel and This isolates the fan case environment from the engine core environment. to high temperature It has silicon as its main component to ensure durability and has the property of maintaining a certain shape. The material used defines the shape of the spherical seal cross-section described above.

This material can withstand high temperatures and has high abrasion resistance, such as densely woven ceramics. Covered by Mick's integument. The fire wall 90 is located between the fan case 30 and the engine. Thickness and flame suppression required to ensure maintenance of Encore 20 isolated environment Made of metal plate or other material with characteristics.

Although the embodiments of the present invention have been described above in detail with reference to the accompanying drawings, the present invention is in no way limited to this particular example (without departing from the scope of the invention). Various modifications and improvements can be made by those skilled in the art.

Copy and translation of written amendment) Submission form (Article 184-8 of the Patent Act) April 15, 1994

Claims (1)

[Claims] 1 An engine core arranged annularly around the longitudinal axis, and this engine core A fan case arranged radially outward in the engine A gas turbine engine including fluid/electrical utility flow means between the core and the In the engine, it includes three sectioned utility distribution harnesses; A first section of the fan case includes a plurality of fan terminals each having a first terminal. and a second section is provided in the engine core 23 for each utility conduit. A third section has a second terminal between the fan case and the engine core. Multiple bridging utilities spanning the annular polygons provided in between each bridging utility conduit has a first terminal and a has a first terminal and a second terminal opposite to the first terminal, and is provided in the fan case. a first terminal of the bridging utility conduit and said bridging utility; a first terminal of the engine conduit; a second terminal of a utility conduit provided in the core and said bridging unit; a second terminal of a utility conduit and a second terminal of the fan cable. utility conduits, bridging utility conduits and engine The utility conduit installed in the gin core is connected between the fan case and the engine core. A gas turbine engine characterized in that a fluid/electricity flow is continuously transmitted to the Njin. 2 An engine core arranged annularly around the longitudinal axis and this engine core A fan case arranged radially outward in the engine A gas turbine engine including fluid/electrical utility flow means between the core and the In the engine, each fan is provided in the fan case and has a first terminal. a plurality of utility conduits each having a second terminal provided in the engine core; the fan case and the engine core; straddles the annular polylume provided between the a second terminal opposite to this first terminal in the null and length direction. multiple bridging utility conduits and these bridging utility conduits. an enclosure disposed about the utility conduit; a first end proximate a first end releasably secured to the fan case; a second end releasably secured to the engine core; the first surface has an opening, and the first surface has an opening, and the first surface has an opening through which the The first terminal provided in the fan case and the bridging utility a first terminal of a conduit, the second surface also having an opening; At the same time, the utility conductor provided in the engine core can be connected through this opening. a second terminal of the conduit and a second terminal of the bridging utility conduit; a utility conduit releasably connected to the fan case; , bridging utility conduits and utilities installed in the engine core. A power conduit provides continuous fluid/electrical flow between the fan case and the engine core. A gas turbine engine that is characterized by being designed to convey information. 3. The gas turbine engine according to claim 2, wherein the enclosure The incoming fluid/electrical flow from the utility conduit can then be routed to different delivery utilities. A gas turbine engine comprising means for directing a gas conduit. 4. The gas turbine engine according to claim 2, wherein the enclosure includes multiple including means for directing a number of outgoing utility flows to a common engine area portion; A gas turbine engine characterized by: 5 An engine core arranged annularly around the longitudinal axis, and this engine core A fan case arranged radially outward in the engine A gas turbine engine including fluid/electrical utility flow means between the core and the In the engine, each fan is provided in the fan case and has a first terminal. a plurality of utility conduits each having a second terminal provided in the engine core; the fan case and the engine core; straddles the annular polylume provided between the a second terminal opposite to this first terminal in the null and length direction. multiple bridging utility conduits and these bridging utility conduits. Enclosures placed around utility conduits and incoming utility conduits means for directing incoming fluid/electrical flow from the , means for directing the plurality of delivered fluid/electrical flows to a common engine section. the enclosure includes a first end releasably secured to the fan case; a first surface proximately disposed and a second end releasably secured to the engine core; a second surface provided adjacent to the first surface, the first surface having an opening; , the first terminal provided in the fan case and the bridge are connected through this opening. a first terminal of the logging utility conduit; The second surface also has an opening and is provided to the engine core through the opening. a second terminal of the bridging utility conduit and said bridging utility conduit; a second terminal of the fan conduit, the second terminal being releasably connected to the second terminal of the fan case; installed utility conduits, bridging utility conduits and engine cores. A utility conduit is provided to route fluid between the fan case and the engine core. /A gas turbine engine characterized by a continuous flow of electricity. hmm. 6. The gas turbine engine according to claim 5, wherein the enclosure includes a flap. a ring extending radially outward from the enclosure at the face of the downstream edge of the fan case; This firewall separates the environment of the fan case from that of the engine core. A gas turbine engine characterized by isolation from